Handbook of Turbomachinery Second Edition Revised - Ventech!

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suppressed that flow separation is almost inevitable in the presence of even small adverse pressure gradients. (See Ref. Haleen and Johnson [9] and Johnston [10]; Session II of Ref. [2] is devoted to this subject.) On the other hand, even small surface asperities in centrifugal compressors can exacerbate friction losses on the high-pressure side. It should be realized that the behavior of the wakes created by rotating blades is also different for the two types of flows. The equations describing the losses due to the wakes are also different. This difference is rarely acknowledged, however, for reasons that are given in the next section. Mixing Losses in One-Directional Flow The flow in axial compressor blades is essentially the flow in curved diffusers. The growth of boundary layers along a blade surface, without secondary flow effects, is shown in Fig. 7. The shaded areas indicate the regions of the retarded flow, which become the wake when it moves downstream of the trailing edges of the blades. (Note that the absolute tangential velocity of the wakes from rotors approaches that of the blades and is usually greater than that of the main stream.) The wake must eventually mix with the main flow. The mass flow rate, flow power, and momentum are conserved during this mixing. Because mixing is an irreversible process, the entropy must increase and a loss in total pressure is suffered. When a frame of reference is available in which the fluid velocity has only one direction, the conserved quantities are expressed by Eq. (11). Note that W ffiffiffiffi p T=AP is proportional to A*=A. W_ ¼ SðP= ffiffiffiffi p TÞcDA ð11aÞ H_ ¼ ScpTDW_ ð11bÞ f ¼ SpmDA ð11cÞ Equation (11c) is a function of the Mach number for uniform flow, and it must be the same as that calculated for nonuniform flow. One can therefore determine the Mach number of the uniform mixed flow with the aid of Eq. (11c). The other properties of the mixed flow can then be determined. If the growth of a boundary layer is calculated, the mixing losses must be included in the loss estimates. If one uses experimental data, note that these data are often the average of the losses in a wake, weighted either by the the incremental mass flow rate of the sample data or by the incremental area. The former underestimates the loss, while the latter overestimates it. How the losses were calculated is thus a necessary guide for the application of the data. Copyright © 2003 Marcel Dekker, Inc.
Figure 7 Boundary layers and wakes formed by cascade elements. (a) Sketch of boundary layers and wakes, (b) velocity distribution along A-A, (c) total-pressure distribution along B-B, (d) total-pressure distribution along C-C. Observe from Fig. 8that boundary layers also form along the outer casing and the hub. Although these boundary layers also represent losses, their principal effect is to block part of the flow area. As previously noted, Eq. (11) is not strictly applicable when there are significant radial components of velocity (Dean and Senoco [11]). It can be Copyright © 2003 Marcel Dekker, Inc.
Page 1 and 2:
D E K K E R Handbook of Turbomachin
Page 3 and 4:
MECHANICAL ENGINEERING A Series of
Page 5 and 6:
61 Computer-Aided Simulation in Rai
Page 7 and 8:
127 Designing for Product Sound Qua
Page 9 and 10:
Preface to the Second Edition The o
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Preface to the Second Edition Prefa
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Contributors Nathan G. Adams The Bo
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1 Introduction Earl Logan, Jr.*, an
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HISTORICAL BACKGROUND Earl Logan, J
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MECHANICAL AND THERMAL DESIGN CONSI
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Figure 1 Cross-section showing the
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Figure 2 Turboprop engine, TPE 331-
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Figure 4 Auxiliary power unit, APU1
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Durability. The mechanical and ther
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with time during flight. Such a typ
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experience and existing similar des
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adverse pressure gradient against w
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and its attachments. A substantial
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Figure 9 Typical high-pressure turb
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and the measurement of local heat-t
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due to cyclic operation. In additio
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the steady and transient conditions
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Table 3(a) Steps in a Three-Dimensi
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Figure 16 Schematic Goodman diagram
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occur due to particles of unburned
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pressures at critical points. These
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1. Ceramics are subject to ‘‘in
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with Transient Tests and Surface Co
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Overall engine performance goals tr
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Much of the complexity of turbomach
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End-wall boundary layers can also h
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pressure at the wake centerline. Th
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the same vaneless diffuser and shro
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from internal cooling passages, thr
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Further downstream, the wake was ev
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to its original position. This unst
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cooling film was found to trip the
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shroud static pressure and the exit
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stage in the design process allows
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Flow Physics Modeling Modeling of t
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passage to the next, assuming that
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The next step in modeling accuracy
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tend to be large, due to the necess
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Navier-Stokes equations are time-ma
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To satisfy these requirements, it i
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are discussed by a number of author
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source code, and to assign each seg
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selected locations in the flow path
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of the component designers must be
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Trends in Flow Modeling Capabilitie
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optimize the flow behavior. The eff
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20. D. Eckardt, ‘‘Flow Field An
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49. K. R. Kirtley, ‘‘An Algebra
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INTRODUCTION 3 Turbine Gas-Path Hea
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Figure 1 Maximum turbine rotor inle
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Figure 2 Intersecting S1 and S2 sur
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determination. Nothing in the simpl
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e well matched with the engine. The
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case different forms of the popular
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volume will be equal to the accumul
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Figure 9 Nusselt number vs. vane su
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Furthermore, to keep computer time
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Figure 12 Comparison of three turbu
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and small and cooled and uncooled t
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Figure 15 Miniature heat flux gauge
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Figure 17 Time resolved heat transf
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Figure 19 Surface pressure changes
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NONUNIFORM INLET FLOW All gas turbi
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Figure 22 Typical distributions of
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4. Better instrumentation for heat-
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24. R. H. Ni, ‘‘A Multiple Grid
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4 Selection of a Gas Turbine Coolin
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Re L ¼ rVL=m—Reynolds number bas
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(1,300 8F). But modern gas turbines
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during engine operation are compati
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Figure 3 Airfoil cooling techniques
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expected to increase this limit to
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1. Reduce the effect of main-stream
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P? is total inlet pressure. Tc=T? i
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thereby increasing both the skin-fr
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After four decades of advancement i
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correspondingly high coolant-side t
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component. Use of a hot cascade for
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nozzle vanes is limited by their ox
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Figure 9 Typical turbine hot sectio
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important factor to consider for tr
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Figure 10 Evolution of nozzle geome
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the exit of the combustor section f
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Figure 12 Inlet turbulence effect o
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in heat transfer as the Reynolds nu
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easonably well using correlations e
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in the section on blade cooling tha
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mass flow rate (e.g., M ¼ 1 for a
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holes. Cooling hole pattern is an i
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coolant flow with the main stream,
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above equation assumes a constant f
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Figure 15 Definition of film-coolin
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edistribution of the external heat-
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Three-Dimensional Effects The three
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In order to achieve the bulk metal
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coefficient is given by Nud ¼ hd=k
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Where G ¼ 2:24ðw=tÞ 0:1 ðReeÞ
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pressure drop. The 608/458 V-shaped
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Some of the studies have found that
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of the cooling air and the turning
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Figure 20 Impingement geometry defi
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correlated by Nu a d ¼ 0:63ðGd=m
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tangentially to the inner wall, beh
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The effectiveness of a suction surf
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vortex structure. Their studies sho
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Figure 23 Effect of preswirler pres
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component to the cooling air that c
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axial gap. A static pressure variat
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Weight, cost, and complexity constr
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Figure 28 Effectiveness of liner co
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thickness. A problem this poses is
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portion of the hole has been shown
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unacceptable engine performance pen
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analysis, in order to provide accur
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Figure 30 Application of PSP for fi
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thermocouple positioned close to th
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spray-painted black (Hallcrest, BB-
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Figure 32 Schematics of a hot casca
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the turbine static temperature (rot
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Figure 33 Experimental rig for inve
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their color when exposed to higher
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margins defined within each discipl
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them. The larger gas-path divergenc
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Figure 36 Blade-cooling selection d
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8. B. Barry, Turbine Blade Cooling:
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40. A. K. Tolpadi and M. E. Crawfor
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73. R. S. Abhari, ‘‘Comparison
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106. J. M. Owen and R. H. Rogers, F
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138. I. Egorov, G. Kretinin, I. Les
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integrity (stress levels) will have
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Figure 1 Instant entropy contours o
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Aerodynamic Interaction (Unsteady L
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Figure 3 Pitchwise time-averaged en
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The above considerations are all fo
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lades, the wavelength of the distur
Page 281 and 282: forcing and damping, and hence the
Page 283 and 284: frequency and its higher harmonics
Page 285 and 286: The two-cell pattern with a relativ
Page 287 and 288: Figure 9 Typical blade flutter boun
Page 289 and 290: field is generated to satisfy the t
Page 291 and 292: Figure 11 Instant static pressure c
Page 293 and 294: Figure 12 Calculated instantaneous
Page 295 and 296: Figure 14 Time-space static pressur
Page 297 and 298: one period Tp (neglecting change of
Page 299 and 300: It should be noted that the effects
Page 301 and 302: There are some further points to no
Page 303 and 304: Figure 17 Flow around an NACA-65 ai
Page 305 and 306: (11) for a simple case]: Where WA
Page 307 and 308: Regardless whether loosely coupled
Page 309 and 310: Several methods have been developed
Page 311 and 312: significant difference is introduce
Page 313 and 314: losses, but it may affect to a mini
Page 315 and 316: when we refine a mesh in an unstead
Page 317 and 318: 8. W. S. Barankiewicz and M. D. Hat
Page 319 and 320: 6 Fundamentals of Compressor Design
Page 321 and 322: Figure 3 AlliedSignal 331 turboprop
Page 323 and 324: each of the selected radii. The pro
Page 325 and 326: components of gas velocity upstream
Page 327 and 328: Observe that each of the curves for
Page 329 and 330: The conservation of angular momentu
Page 331: allowable static pressure ratio of
Page 335 and 336: component that is perpendicular to
Page 337 and 338: Figure 10 (a) Deflection of flow of
Page 339 and 340: increase in the downstream pressure
Page 341 and 342: Mach number at a compressor outlet
Page 343 and 344: Figure 12 Sketch of flow surface an
Page 345 and 346: useful shapes and orientations of b
Page 347 and 348: where G and oa are constant along a
Page 349 and 350: There is a good reason for this sit
Page 351 and 352: Projected Shape in Meridional Plane
Page 353 and 354: inherent flow range of the impeller
Page 355 and 356: compressors. Multistage centrifugal
Page 357 and 358: turbines. In these designs the high
Page 359 and 360: Corrections for Streamline Curvatur
Page 361 and 362: Preparation of Maps Once the losses
Page 363 and 364: that circumferential gradients meas
Page 365 and 366: Nastran, which was developed by NAS
Page 367 and 368: tests. One should take pains to pro
Page 369 and 370: e predicted in advance. Total press
Page 371 and 372: Cv Coefficient of heat at constant
Page 373 and 374: 15. S. Lieblein, J. Basic Eng., Tra
Page 375 and 376: INTRODUCTION 7 Fundamentals of Turb
Page 377 and 378: Figure 1 Cross sections of generic
Page 379 and 380: espectively. Radial-inflow turbines
Page 381 and 382: Figure 4 Typical rotor blade shapes
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Figure 6 The expansion process acro
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the average for the gas flowing thr
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etween the velocity diagram and the
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gas dynamics relation p 00 p ¼ T 0
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Figure 9 Variations in turbine velo
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pressure, inlet losses are usually
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diffuser recovery, defined as Rp ¼
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different turbines easier, dimensio
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where and y ¼ T 0 in TSTD d ¼ p0
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sizing exercises where the details
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where Rth is the Reynolds number ba
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order to determine the overall turb
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The classical approach to satisfyin
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clearance. Since tip clearance repr
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turbine with an effective diffuser,
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atio ðp 0 in =pdisÞ is 3. The sta
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Automation of Calculations and Trad
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and for the rotor Zrotor ¼ ð0:1Þ
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the energy extracted and the rotor
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RADIAL-INFLOW TURBINE SIZING Differ
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interpolations from existing design
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Glassman [1], the optimum ratio of
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design fault in the radial-inflow t
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[27]. In order to avoid manufacturi
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The rotor exit critical velocity is
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The hub-to-tip radius ratio at the
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REFERENCES 1. A. J. Glassman (ed.),
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8 Steam Turbines Thomas H. McCloske
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Figure 3 Reciprocating steam engine
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This process began in the 1920s, al
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First Law of Thermodynamics The fir
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the amount of fuel burned and the p
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Figure 7 Rankine cycle temperature-
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The Mollier diagram is quite useful
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Figure 10 Theoretical Rankine cycle
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stages of the turbine is at a highe
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calculate the relevant thermodynami
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Figure 14 Steam leakage losses for
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can reveal nozzle and/or blade eros
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Figure 17 Enlarged portion of the M
Page 463 and 464:
Traditionally, pressures have been
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Figure 21 Wetness thermodynamic los
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Figure 23 Radial steam turbine flow
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Figure 25 Percentage stage reaction
Page 471 and 472:
The power output of the stage can b
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the LP turbines is split into paral
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Turbine Inlet Two stages in particu
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of 20%, which would cause excessive
Page 479 and 480:
Figure 30 Typical low-pressure stea
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ductility and poor toughness, since
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‘‘tramp’’ elements to minim
Page 485 and 486:
End Seals End seals or packing glan
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Drains Condensate can form during s
Page 489 and 490:
Figure 32 Steam turbine blade roots
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Figure 34 Cross-section view of thr
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Figure 36 Interblade shroud and Tie
Page 495 and 496:
Where The influence of notch sensit
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Similarly, LP turbine blades are su
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those made of steel. Note, however,
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esult, significant attention must b
Page 503 and 504:
Figure 38 Centrifugal stresses on a
Page 505 and 506:
Figure 39 Centrifugal bending stres
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onto the rotating blade. These can
Page 509 and 510:
Vortex shedding from blade trailing
Page 511 and 512:
Figure 42 Torsional coupled vibrati
Page 513 and 514:
Figure 44 Stall flutter of low-pres
Page 515 and 516:
Start-Stop Transients/Overspeeds La
Page 517 and 518:
(4) ellipiticity, such as caused by
Page 519 and 520:
Figure 47 Campbell diagram (frequen
Page 521 and 522:
Furthermore, in practice each manuf
Page 523 and 524:
Figure 49 Modal diameters of a low-
Page 525 and 526:
Figure 51 Three-dimensional computa
Page 527 and 528:
Figure 52 Converging wedge and resu
Page 529 and 530:
value as the operating value of uv/
Page 531 and 532:
Lubrication Supply System Design De
Page 533 and 534:
Figure 56 Steam turbine oil system
Page 535 and 536:
The main oil reservoir is located b
Page 537 and 538:
Although a light oil does provide a
Page 539 and 540:
temperatures are suspected as reaso
Page 541 and 542:
There is no fixed or absolute value
Page 543 and 544:
pivots incorporated in this bearing
Page 545 and 546:
covers and doors. Pipe scale, rust,
Page 547 and 548:
Figure 63 Mechanical hydraulic cont
Page 549 and 550:
Figure 64 Steam turbine electro-hyd
Page 551 and 552:
Figure 65 Steam turbine electro-hyd
Page 553 and 554:
generator rotor moment of inertia h
Page 555 and 556:
the turbine against overspeed. This
Page 557 and 558:
an additional electronic overspeed
Page 559 and 560:
Figure 68 Steam turbine protective
Page 561 and 562:
3. Need for better understanding of
Page 563 and 564:
REFERENCES 1. J. C. Zink, ‘‘Ste
Page 565 and 566:
No. TWDPS-1, The American Society o
Page 567 and 568:
58. A. V. Sarlashkar and T. C. T. L
Page 569 and 570:
81. IEEE Guide for Abnormal Frequen
Page 571 and 572:
Atlanta, GA, Oct. 18-22, 1992, PWR-
Page 573 and 574:
Performance Enhancement Program, he
Page 575 and 576:
of the design process toward achiev
Page 577 and 578:
procedure capable of addressing mul
Page 579 and 580:
to achieve a specific target pressu
Page 581 and 582:
objective was to minimize the downs
Page 583 and 584:
more closely represents the largest
Page 585 and 586:
temperature by forming a thin film
Page 587 and 588:
such as the one described here. For
Page 589 and 590:
k is the thermal conductivity of th
Page 591 and 592:
through finite differences. Mathema
Page 593 and 594:
Figure 4 Comparison of blade cross-
Page 595 and 596:
integration of multiple disciplines
Page 597 and 598:
17. S. S. Talya, ‘‘Multidiscipl
Page 599 and 600:
INTRODUCTION 10 Rotordynamic Consid
Page 601 and 602:
Figure 1 (c) AlliedSignal 331 turbo
Page 603 and 604:
Figure 2 Rotor system displacements
Page 605 and 606:
Figure 3 Elliptic lateral whirl. av
Page 607 and 608:
vibration (either forward or backwa
Page 609 and 610:
Figure 6 The Laval-Jeffcott rotor.
Page 611 and 612:
are 1808 out of phase (i.e., the be
Page 613 and 614:
this graph is quite simple; however
Page 615 and 616:
included on these types of graphs b
Page 617 and 618:
on the shaft is zero. Thus, the ste
Page 619 and 620:
are uðtÞ ¼e zeott uo cos ott þ
Page 621 and 622:
satisfies the inequality O < ot 1
Page 623 and 624:
Figure 16 Laval-Jeffcott rotor tran
Page 625 and 626:
Figure 18 Whirl speed map: Laval-Je
Page 627 and 628:
Figure 20 Laval-Jeffcott rotor: ste
Page 629 and 630:
Figure 22 Typical precessional mode
Page 631 and 632:
Figure 24 Examples of flexible disk
Page 633 and 634:
ackward modes, however, involve con
Page 635 and 636:
Figure 29 Steady unbalance response
Page 637 and 638:
assist in attenuating high vibratio
Page 639 and 640:
properly sizing the damper, a highl
Page 641 and 642:
Figure 31 Gas turbine schematic and
Page 643 and 644:
Flexible Disk If the frequency of a
Page 645 and 646:
motion for each subsegment to form
Page 647 and 648:
Figure 35 Whirl speed map—straddl
Page 649 and 650:
Figure 37 Rotor-bearing-support str
Page 651 and 652:
DESIGN STRATEGIES AND PROCEDURES Ro
Page 653 and 654:
Figure 38 Straddle mounted rotor. (
Page 655 and 656:
Figure 39 Unbalance response: strad
Page 657 and 658:
Figure 40 Double overhung rotor—d
Page 659 and 660:
earing supports are reduced. The th
Page 661 and 662:
and also increases the critical spe
Page 663 and 664:
Examples of structure modes couplin
Page 665 and 666:
REFERENCES 1. D. Childs, Turbomachi
Page 667 and 668:
section is intended to place today
Page 669 and 670:
pressure-fed propellant systems. Hi
Page 671 and 672:
normally be considered a very small
Page 673 and 674:
increase of required suction perfor
Page 675 and 676:
displaced by the F-1 oxidizer pump
Page 677 and 678:
exposure may be subjected to imping
Page 679 and 680:
the exhaust duct. Sized to create s
Page 681 and 682:
excess of 6,000 psi for consumption
Page 683 and 684:
lifetime. With very few exceptions,
Page 685 and 686:
using hydrocarbon fuel combustion p
Page 687 and 688:
can yield noticeable savings in req
Page 689 and 690:
Figure 3 Rocket engine system schem
Page 691 and 692:
Figure 6 Staged combustion system,
Page 693 and 694:
each stage. The term C0 represents
Page 695 and 696:
Figure 10 Some representative turbo
Page 697 and 698:
emembered that the second (and any
Page 699 and 700:
the greatest demands on turbopump p
Page 701 and 702:
momentum exchange between working f
Page 703 and 704:
Figure 13 Arrangement of various tu
Page 705 and 706:
pressure levels. As long as combust
Page 707 and 708:
Figure 14 Approxmate values of pump
Page 709 and 710:
liquid rocket engine systems, and e
Page 711 and 712:
above becomes a factor. This statem
Page 713 and 714:
We can then state (correctly) that,
Page 715 and 716:
Figure 15c Typical 2-D centrifugal
Page 717 and 718:
have seen that the flow rate throug
Page 719 and 720:
somewhat smaller magnitude of vecto
Page 721 and 722:
general indicator. Nss will give us
Page 723 and 724:
U ¼ rotor tangential velocity. By
Page 725 and 726:
and pump flow derived from the engi
Page 727 and 728:
In addition to shaft seals, shaft b
Page 729 and 730:
should be understood that the optim
Page 731 and 732:
stable operation is assured. In som
Page 733 and 734:
From Eq. (16) an impeller radial ou
Page 735 and 736:
Figure 18 Examples of centrifugal p
Page 737 and 738:
tional to clearance distance) with
Page 739 and 740:
I would like to conclude this secti
Page 741 and 742:
generally result in lower pump hydr
Page 743 and 744:
Figure 15h Cross-section of a typic
Page 745 and 746:
solutions of Eq. (7) for both stage
Page 747 and 748:
Figure 15k H-Q characteristics for
Page 749 and 750:
Figure 15l Typical inducer configur
Page 751 and 752:
camber) is proportionally lower. Th
Page 753 and 754:
Figure 22 Single-stage impulse turb
Page 755 and 756:
the velocity ratio K, but in somewh
Page 757 and 758:
~V and ~n ¼ fluid velocity and con
Page 759 and 760:
Fig. 25. The nature of the flow in
Page 761 and 762:
Although shrouded centrifugal impel
Page 763 and 764:
is a parasitic device, whose flow r
Page 765 and 766:
apidly than does the inducer thrust
Page 767 and 768:
Figure 30 LH2 turbopump rotor mecha
Page 769 and 770:
eplacement of a failed bearing with
Page 771 and 772:
shall see, contemporary rocket engi
Page 773 and 774:
needs of the aircraft gas turbine a
Page 775 and 776:
was increased due to engine upratin
Page 777 and 778:
12 Turbomachinery Performance Testi
Page 779 and 780:
istics. The more accurate the perfo
Page 781 and 782:
Inlet Distortion Most turbomachiner
Page 783 and 784:
Gas Thermodynamic Properties Turbom
Page 785 and 786:
ought to rest isentropically. Total
Page 787 and 788:
include not only the pressure chang
Page 789 and 790:
The circumferential placement of th
Page 791 and 792:
simply arithmetically averaging the
Page 793 and 794:
usually mounted in radial immersion
Page 795 and 796:
Figure 12(b) Radial flow angle prof
Page 797 and 798:
Figure 15 Wake rake total pressure
Page 799 and 800:
Figure 16 Blade-tip pressure traces
Page 801 and 802:
Figure 18 Typical test rig schemati
Page 803 and 804:
INSTRUMENTATION DESIGN CONSIDERATIO
Page 805 and 806:
Dynamic Pressure. Dynamic pressure
Page 807 and 808:
thermocouples. With care in constru
Page 809 and 810:
Figure 24 Typical two-dimensional f
Page 811 and 812:
Thermocouple lead wires should be i
Page 813 and 814:
Corrected Flow The flow rates used
Page 815 and 816:
pressure ratio [15]. It can be calc
Page 817 and 818:
SYMBOLS A Cross-section area Cd Dis
Page 819 and 820:
INTRODUCTION 13 Automotive Supercha
Page 821 and 822:
Figure 2 A Roots-type supercharger
Page 823 and 824:
The supercharger was in routine use
Page 825 and 826:
Table 1 Superchargers Versus Turboc
Page 827 and 828:
1960s, turbocharging was used by US
Page 829 and 830:
Roots Blower The Roots-type blower
Page 831 and 832:
speeds. The sound is caused by the
Page 833 and 834:
Figure 8b How the Ro-charger operat
Page 835 and 836:
The vanes in many designs are preve
Page 837 and 838:
Figure 11a Key components of the G-
Page 839 and 840:
Figure 11c G-Lader supercharger is
Page 841 and 842:
Figure 12b Schematic of centrifugal
Page 843 and 844:
Figure 14b Components of the typica
Page 845 and 846:
Turbine Design The turbine housing
Page 847 and 848:
inertia of the wheel assembly. Mini
Page 849 and 850:
Figure 18 (a) Turbocharger compress
Page 851 and 852:
Theoretically this efficiency is: o
Page 853 and 854:
The overall turbine efficiency incl
Page 855 and 856:
adjust the spring force to vary the
Page 857 and 858:
Figure 22b Two vanes are used to pr
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However, the temperature has to be
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air can reduce carbon monoxide and
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Figure 25 (a) Schematic of the COMP
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this plus the fact that the exhaust
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14 Tesla Turbomachinery Warren Rice
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press at the time of the invention
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can be made to simplify the equatio
Page 873 and 874:
comparison of the results of variou
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y composing them of nested cones ra
Page 877 and 878:
26. E. Bakke, ‘‘Theoretical and
Page 879 and 880:
61. M. Piesche, ‘‘Investigation
Page 881 and 882:
15 Hydraulic Turbines V. Dakshina M
Page 883 and 884:
Table 1 Variables of Interest in Tu
Page 885 and 886:
Figure 1 Variation of impeller shap
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Figure 2 Flow and velocity componen
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Figure 3 Schematic diagram of Pelto
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shown in Fig. 5(see KadambiandPrasa
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classified according to the directi
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The manufacturers of hydraulic turb
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The direction of the relative veloc
Page 899 and 900:
Table 3 Variation of Some Quantitie
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denoted by hd. Thus the efficiency
Page 903 and 904:
Figure 14 Draft tube setting. same
Page 905:
REFERENCES 1. J. J. Fritz, Small an
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Handbook of Turbomachinery Second Edition Revised - Ventech!

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